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Tuesday, May 5, 2020 | History

4 edition of Pegasus wing-glove experiment to document hypersonic crossflow transition found in the catalog.

Pegasus wing-glove experiment to document hypersonic crossflow transition

Pegasus wing-glove experiment to document hypersonic crossflow transition

measurement system and selected flight results

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Published by National Aeronautics and Space Administration, Dryden Flight Research Center, NASA Center for AeroSpace Information [distributor], National Technical Information Service [distributor in Edwards, Calif, Hanover, MD, Springfield, Va .
Written in English


Edition Notes

Other titlesPegasus wing glove experiment to document hypersonic crossflow transition.
StatementArild Bertelrud ... [et al.].
Series[NASA technical memorandum] -- NASA/TM-2000-209016., NASA technical memorandum -- 209016.
ContributionsBertelrud, Arild., Hugh L. Dryden Flight Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL17593819M
OCLC/WorldCa43761689

pegasus® wing-glove experiment to document hypersonic crossflow transition—measurement system and selected flight results, technical memorandum Authors: Arild Bertelrud, Geva de la Tova, Philip J. Hamory, Ronald Young, Gregory K. Noffz, Michael Dodson, Sharon S. Graves, John K. Diamond, James E. Bartlett, Robert Noack and David Knoblock. The goal of this paper is to develop rationale for new hypersonic boundary layer transition flight experiments. Motivations will be derived from both an inward look at what we believe constitutes a good flight test program as well as an outward review of the goals and objectives of some recent US based unclassified proposals and programs.

The first phase is a matrix of inlet characterization (IC) tests to evaluate the inlet performance and establish the mode transition schedule. The second phase is a matrix of dynamic system identification (SysID) experiments designed to support closed-loop control development at mode transition schedule operating points for the CCE-LIMX. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Cited by:

Pegasus was been used to launch a number of satellites and the PHYSX experiment. That experiment consisted of a smooth glove installed on the first-stage delta wing of the Pegasus. The glove was used to gather data at speeds of up to Mach 8 and at altitudes approaching , feet. transition onset and at the characteristic roughness height. For small roughness, the elements can be assumed to be at the wall temperature, hence, the fluid viscosity is evaluated at the wall temperature. The transition correlation of Reda, et al.3 for blunt bodies with distributed roughness in hypersonic flight through air is shown in Fig. Size: 1MB.


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Pegasus wing-glove experiment to document hypersonic crossflow transition Download PDF EPUB FB2

In a recent flight experiment to study hypersonic crossflow transition, boundary layer characteristics were documented. A smooth steel glove was mounted on the first stage delta wing of Orbital Sciences Corporation's Pegasus ® launch vehicle and was flown at speeds of up to Mach 8 and altitudes of up toft.

The wing-glove experiment was flown as a secondary payload offCited by: 3. Pegasus wing-glove experiment to document hypersonic crossflow transition - Measurement system and selected flight results Arild Bertelrud, Geva de la Tova. Pegasus wing-glove experiment to document hypersonic crossflow transition - Measurement system and selected flight results.

Arild Bertelrud, Geva de la Tova, Philip Hamory, Ronald Young, Gregory Noffz, Michael Dodson, Sharon Graves, John Diamond, James Bartlett, Robert Noack and al e. In a recent flight experiment to study hypersonic crossflow transition, boundary layer characteristics were documented.

A smooth steel glove was mounted on the first stage delta wing of Orbital Sciences Corporation's Pegasus launch vehicle and was flown at speeds of up to Mach 8 and altitudes of up toft. In a recent flight experiment to study hypersonic crossflow transition, boundary layer characteristics were documented.

A smooth steel glove was mounted on the first stage delta wing of Orbital Sciences Corporation's Pegasus ® launch vehicle and was flown at speeds of up Aerospace Engineer, Member MAA?Instrumentation Engineer +Instrumentation EngineerCited by: 3. Pegasus(Registered trademark) Wing-Glove Experiment to Document Hypersonic Crossflow Transition: Measurement System and Selected Flight Results Article (PDF Available).

In a recent flight experiment to study hypersonic crossflow transition, boundary layer characteristics were documented. A smooth steel glove was mounted on the first stage delta wing of Orbital Sciences Corporation's Pegasus (R) launch vehicle and was flown at speeds of up to Mach 8.

In a recent flight experiment to study hypersonic crossflow transition, boundary layer characteristics were documented. A smooth steel glove was mounted on the first stage delta wing of Orbital Sciences Corporation's Pegasus® launch vehicle and was flown at speeds of up to Mach 8 and altitudes of up toft.

Pegasus(Registered trademark) Wing-Glove Experiment to Document Hypersonic Crossflow Transition: Measurement System and Selected Flight Results Article Full-text available.

CROSSFLOW STABILITYAND TRANSITION _i EXPERIMENTS INA SWEPT-WING FLOW by J. Ray Dagenhart Dissertation submitted to the Faculty of the Virginia Polytechnic Institute and State University in partial fulfillment of the requirements for the degree of Doctor of Philosophy in Engineering Mechanics Dr.

Saric, Co-chairman Dr. Cramer Dr. Transition prediction of a yawed cylinder has been performed by the γ-Reθ transition model with the proposed crossflow criterion.

The production of eddy viscosity due to the present criteria was. In a recent flight experiment to study hypersonic crossflow transition, boundary layer characteristics were documented. A smooth steel glove was mounted on the first stage delta wing of Orbital Sciences Corporation's Pegasus launch vehicle and was flown at speeds of up to Mach 8 and altitudes of up toft.

A hypersonic flight test to document laminar/turbulent transition. Pegasus wing-glove experiment to document hypersonic crossflow transition - Measurement system and selected flight results James Bartlett, Robert Noack and al e; 38th Aerospace Sciences Meeting and Exhibit August Pegasus wing-glove experiment to document crossflow.

Computational fluid dynamics methods were used in the design of a wing shape for study of hypersonic crossflow transition in flight.

The flight experi Cited by: Abstract. Low speed experiments were conducted to study features of crossflow transition on the windward surface of a wing swept at 40°. Surface pressure and wall shear stress fluctuation measurements and flow visualization by chemical sublimation conducted at different incidence angles revealed both stationary vortices and TS : V.

Krishnan, R. Mukund, P.R. Viswanath. Pegasus wing-glove experiment to document hypersonic crossflow transition: measurement systems and selected flight results Author: Arild Bertelrud ; Hugh L.

Dryden Flight Research Center. Pegasus wing-glove experiment to document hypersonic crossflow transition: measurement system and selected flight results Author: Arild Bertelrud ; Hugh L. Dryden Flight Research Center. Shock-wave shapes around spherical-and cylindrical-nosed bodies.

Laminar to turbulent transition prediction in hypersonic flows with neural networks committee. Pegasus wing-glove experiment to document crossflow transition - Development and current by: Pegasus(Registered trademark) Wing-Glove Experiment to Document Hypersonic Crossflow Transition: Measurement System and Selected Flight Results Citing article Feb In his remarkable memoir Runway to Orbit, Dr.

Kenneth W. Iliff - the recently retired Chief Scientist of the NASA Dryden Flight Research Center- tells a highly personal, yet a highly persuasive account of the last forty years of American aeronautical research. His interpretation of events commands respect, because over these years he has played pivotal roles in many of the most important.

EXTENSIONS OF MENTER’S SST TRANSITION MODEL TO SIMULATE HYPERSONIC AND CROSS-FLOW TRANSITION F Re qclength LT υ 7 42 θc t 13 LT θt Re Re 10 Re 10 Re Re 10 Re The Re t equation is designed to introduce the free-stream information into the boundary layer as the criterion of transition onset position.Experimental Study on Hypersonic Pitch-Up Anomaly in Shock Tunnel Pegasus Wing-Glove Experiment to Document Hypersonic David Knoblock; In a recent flight experiment to study.Mack’s first- and second-mode streamwise instabilities, crossflow instabilities in 3D boundary layers, and Görtler instability over regions of concave curvature.

For hypersonic flows, the region between the onset of transition and the onset of fully developed turbulent flow (i.e., the transition region) can be quite long, sometimes of theCited by: